Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(oaf117-il) OAF117 AIRFOIL | ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord | Remove Airfoil details Airfoil plotter |
(goe477-il) GOE 477 AIRFOIL | Gottingen 477 airfoil Max thickness 10.1% at 30% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(n24-il) N-24 | N-24 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(ag26-il) AG26 Bubble Dancer DLG by Mark Drela | Drela AG26 airfoil used on the Bubble Dancer R/C DLG Max thickness 6.8% at 23.3% chord Max camber 2.5% at 45.5% chord | Remove Airfoil details Airfoil plotter |
(e655-il) EPPLER 655 AIRFOIL | Eppler E655 sailplane airfoil Max thickness 17.3% at 37.3% chord Max camber 3.9% at 42.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (oaf117-il,goe477-il,n24-il,ag26-il,e655-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf117-il | 50,000 | 9 | 28.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 50,000 | 5 | 34.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 9 | 46.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 5 | 49.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 9 | 64.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 5 | 63 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 9 | 84.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 5 | 78.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 9 | 96.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 5 | 89.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 50,000 | 9 | 34.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 50,000 | 5 | 36.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 100,000 | 9 | 56.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 100,000 | 5 | 54.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 200,000 | 9 | 80.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 200,000 | 5 | 75 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 500,000 | 9 | 111.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 500,000 | 5 | 87.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 1,000,000 | 9 | 121.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 1,000,000 | 5 | 104.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 50,000 | 9 | 6.5 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 50,000 | 5 | 24.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 100,000 | 9 | 41.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 100,000 | 5 | 47 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 200,000 | 9 | 65.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 200,000 | 5 | 64.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 500,000 | 9 | 91.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 500,000 | 5 | 84.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n24-il | 1,000,000 | 9 | 108.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n24-il | 1,000,000 | 5 | 104.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag26-il | 50,000 | 9 | 36.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag26-il | 50,000 | 5 | 39.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag26-il | 100,000 | 9 | 54.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag26-il | 100,000 | 5 | 53.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag26-il | 200,000 | 9 | 71.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag26-il | 200,000 | 5 | 65.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag26-il | 500,000 | 9 | 91.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag26-il | 500,000 | 5 | 83 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag26-il | 1,000,000 | 9 | 104.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag26-il | 1,000,000 | 5 | 96 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 50,000 | 9 | 4.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 50,000 | 5 | 14.6 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 100,000 | 9 | 36.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 100,000 | 5 | 30.7 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 200,000 | 9 | 69.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 200,000 | 5 | 69.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 500,000 | 9 | 116.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 500,000 | 5 | 111.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 1,000,000 | 9 | 150.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 1,000,000 | 5 | 135.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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